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在对国内外流场与结构温度场一体化计算方法的不足进行细致讨论的基础上,提出了一种高超声速流场与结构温度场一体化计算方法.采用统一的积分方程组作为气动加热和结构传热物理过程的控制方程,对整个物理场进行统一的迎风格式有限体积方法离散,给出了流场与结构交界面上温度、温度梯度及导热系数等参数的计算方法.在时间推进方面,定常状态采用多步龙格库塔迭代格式,非定常状态则采用双时间步长方法.采用发展的一体化算法对二维圆管模型的气动加热和结构传热问题进行了数值模拟.结果表明:2s时驻点物面温度为390K,与其他文献的误差在3.1K范围内;稳定时驻点物面温度为647K.
Based on the detailed discussion of the deficiencies of the integration of flow field and structure temperature field at home and abroad, an integrated calculation method of hypersonic flow field and structure temperature field is proposed. The control equations of the physical structure of the heat transfer process, the unified finite volume method of the upwind scheme is discretized for the whole physical field, and the calculation methods of temperature, temperature gradient and thermal conductivity on the interface between the flow field and the structure are given. , The multi-step Runge-Kutta iterative scheme is adopted for the steady state, and the double time step method is used for the unsteady state.The aerodynamic heating and heat transfer of two-dimensional circular tube model are numerically simulated by the developed integrated algorithm.Results The results show that the surface temperature of the stationary point is 390K at 2s, and the error with other references is within 3.1K. The stationary surface temperature at stationary point is 647K.